CN103459776A

CN103459776A - Vane member and rotary machine

Info

Publication number: CN103459776A
Application number: CN201280014878XA
Authority: CN
Inventors: 桑原正光
Original assignee: Mitsubishi Heavy Industries Ltd
Current assignee: Mitsubishi Power Ltd
Priority date: 2011-04-22
Filing date: 2012-01-26
Publication date: 2013-12-18
Anticipated expiration: 2032-01-26
Also published as: KR20130122689A; EP2700787A4; EP2700787A1; US20120269615A1; JP5852208B2; US9181807B2; KR101543141B1; EP2700787B1; JPWO2012144244A1; JP2015025458A; CN103459776B; WO2012144244A1; JP5655210B2

Abstract

The airfoil member of the present invention is provided with an airfoil body, an end wall which is installed at an end part of the airfoil body in a blade span direction and extends so as to intersect in the blade span direction, a fillet portion which smoothly connects the end part of the airfoil body with the end wall, and a cooling channel which allows a cooling medium to circulate inside the airfoil body and the end wall and in which two main channels extending along the blade span direction are connected so as to bend in a folding manner at a return channel formed on the end wall side. The return channel is formed so as to run along the fillet portion on a cross section intersecting with a center line of a profile of the airfoil body and also formed in such a manner that the width thereof in the profile thickness direction is greater than the width of the main channel in the profile thickness direction.

Description

Blade part and rotating machinery

Technical field

The present invention relates to blade part and rotating machinery.

Background technique

As everyone knows, blade part is one of most important key element in rotating machinery.For example, be located at the blade part of stator side as working fluid is carried out the stator blade of rectification and brings into play function.And, be located at the blade part of rotor-side as from the working fluid recovered energy or to working fluid, the moving vane of energy being provided and bringing into play function.

When under hot environment, using this blade part, the oxidation attenuate, the fatigue that in order to be suppressed at blade part, produce, need to carry out cooling to blade part.

For example, the stator blade that following patent documentation 1 is put down in writing possesses: the blade body extended along the turbine radial direction; With the front end that is formed at this blade body the end wall that extends in the mode of intersecting with the turbine radial direction, be formed with snakelike stream in the inside of blade body, a plurality of cooling flowing paths that this snakelike stream will extend along the turbine radial direction respectively connect into tortuous shape.And, circulate in this snakelike stream by making cooling-air, and realize the cooling of blade part.

Moving vane in following patent documentation 2 has adopted same cooling flowing path.

Patent documentation 1: Japanese kokai publication hei 10-299409 communique

Patent documentation 2: TOHKEMY 2006-170198 communique

Summary of the invention

Yet, in above-mentioned blade part, as shown in FIG. 13 and 14, cooling-air c mobile in snakelike stream 74 carries out cooling from inboard to blade body 70.

But in above-mentioned blade part, usually be formed with fillet part 73, this fillet part 73 is by the end 71(base portion of blade body 70) with end wall 72(platform) be connected smoothly.Therefore, as shown in figure 14, at the periphery generation position large to the wall thickness of the blade wall of the outer surface of fillet part 73 from the reflex part 75 of snakelike stream 74 of fillet part 73.Thus, the large position at this blade wall wall thickness, likely can't come by cooling-air c fully cooling.

The present invention makes under the circumstances, and problem is to carry out fully the cooling of fillet part.

Blade part of the present invention possesses: blade body; End wall, be located at the end on the width of blade direction of above-mentioned blade body, and extend in the mode of intersecting with above-mentioned width of blade direction; Fillet part, be connected the end of above-mentioned blade body smoothly with above-mentioned end wall; And cooling flowing path, make the internal circulation of cooling medium at above-mentioned blade body and above-mentioned end wall, and two primary flow path of extending along above-mentioned width of blade direction are connected in the mode bent by the stream that turns back that is formed at above-mentioned end wall side, in above-mentioned blade part, the above-mentioned stream that turns back forms in the mode along above-mentioned fillet part on the cross section intersected with the aerofoil profile center line of above-mentioned blade body, and the width on the vane thickness direction of the above-mentioned stream that turns back forms greatlyr than the flow path width on the vane thickness direction of above-mentioned primary flow path.

So, the stream that turns back forms in the mode along fillet part on the cross section intersecting with the aerofoil profile center line, therefore roughly even to the wall thickness of the outer surface of fillet part from the stream that turns back.Thus, can suppress to produce this situation of wall thickness increase position of blade wall, thereby can evenly and fully carry out cooling to fillet part.

And the above-mentioned stream that turns back has the heat-absorbent surface formed along the outer surface of above-mentioned fillet part in surface within it.

So, owing to thering is heat-absorbent surface, therefore can to the fillet part back to this heat-absorbent surface, carry out cooling more fully.

And the above-mentioned stream that turns back can have protuberance, this protuberance is formed at the center side of the vane thickness direction of above-mentioned blade body, and the flow direction of above-mentioned cooling medium is guided to above-mentioned vane thickness direction both sides.

So, owing to having protuberance, so cooling medium is directed to vane thickness direction both sides.Thus, can be fully to the fillet part of the vane thickness direction both sides that are positioned at the stream that turns back, carry out cooling.

And the above-mentioned stream that turns back can possess Cooling Holes on the partition wall between the upstream side stream in itself and above-mentioned primary flow path, wherein the upstream side stream in above-mentioned primary flow path is positioned at the upstream side of the above-mentioned stream that turns back.

So, at the pressurized air of the heat-absorbent surface Flow Structure Nearby of the stream that turns back, be updated, the cooling performance of heat-absorbent surface further improves.

And above-mentioned heat-absorbent surface can form with the outer surface from above-mentioned blade body roughly the same to the distance of the internal surface of above-mentioned primary flow path apart from the distance of the outer surface of above-mentioned fillet part.

So, because the distance of the outer surface of the fillet part of distance heat-absorbent surface forms with the outer surface from blade body roughly the samely to the distance of the internal surface of primary flow path, therefore can between blade body and fillet part, carry out equably cooling.

And above-mentioned heat-absorbent surface can extend along above-mentioned aerofoil profile center line.

So, because heat-absorbent surface extends along the aerofoil profile center line, therefore can along the aerofoil profile center line on a large scale in evenly and fully to fillet part, carry out cooling.

And rotating machinery of the present invention possesses above-mentioned blade part.

So, owing to possessing above-mentioned blade part, therefore can improve the cooling effect of blade part, the rotating machinery that a kind of reliability is high is provided.

The invention effect

According to blade part of the present invention, can evenly and fully carry out cooling at fillet part.

And, according to rotating machinery of the present invention, can improve reliability.

The accompanying drawing explanation

Fig. 1 means the half sectional view of schematic configuration of the gas turbine GT of the first mode of execution of the present invention.

Fig. 2 be the first mode of execution of the present invention turbine T want section's amplification view, be the enlarged view of wanting the I of section of Fig. 1.

Fig. 3 is the dissecing and the sectional view that forms along aerofoil profile center line Q of turbine moving blade 3 of the first mode of execution of the present invention, is the II-II line sectional view in Fig. 4.

Fig. 4 is the aerofoil profile sectional view intersected with the width of blade direction of the turbine moving blade 3 of the first mode of execution of the present invention, is the III-III line sectional view in Fig. 3.

Fig. 5 be the first mode of execution of the present invention moving vane 3 want section's amplification view, be the enlarged view of wanting the IV of section of Fig. 3.

Fig. 6 is the sectional view intersected with aerofoil profile center line Q of the cooling flowing path 50 of the first mode of execution of the present invention, is the V-V line sectional view of Fig. 5.

Fig. 7 is the sectional view intersected with aerofoil profile center line Q of the cooling flowing path 50 of the first mode of execution of the present invention, is the VI-VI line sectional view of Fig. 5.

Fig. 8 is the dissecing and the sectional view that forms along the aerofoil profile center line of turbine stator vane 2 of the second mode of execution of the present invention.

Fig. 9 means the dissecing and the sectional view that forms along aerofoil profile center line Q of turbine moving blade 3 of the 3rd mode of execution of the present invention.

Figure 10 be Fig. 9 want section's enlarged view (enlarged view of wanting the VII of section of Fig. 9).

Figure 11 is the sectional view of the cooling flowing path of the 3rd mode of execution of the present invention, is the VIII-VIII line sectional view of Figure 10.

Figure 12 is the sectional view of the cooling flowing path of the 3rd mode of execution of the present invention, is the IX-IX line sectional view of Figure 11.

Figure 13 is the longitudinal sectional view of existing turbine moving blade.

Figure 14 is the X-X line sectional view in Figure 13.

Embodiment

Below, with reference to accompanying drawing, embodiments of the present invention are described.

(the first mode of execution)

Fig. 1 means the half sectional view of schematic configuration of gas turbine (rotating machinery) GT of the first mode of execution of the present invention.As shown in Figure 1, gas turbine GT possesses: compressor C generates pressurized air (cooling medium) c; A plurality of burner B, generate combustion gas g to the pressurized air c feed fuels of supplying with from compressor C; And turbine (rotating machinery) T, obtain rotating power by the combustion gas g supplied with from burner B.

In gas turbine GT, the rotor R of compressor C _crotor R with turbine T _tconnect and extend on turbine shaft P at axle head separately.

In addition, in the following description, by rotor R _tbearing of trend be called turbine shaft to, by rotor R _tcircumferencial direction to be called turbine circumferential, by rotor R _tradial direction be called turbine radially.

Fig. 2 be turbine T want section's amplification view, be the enlarged view of wanting the I of section of Fig. 1.

As shown in Figure 2, turbine T possesses in turbine shroud 1 along turbine shaft to the turbine stator vane 2 that alternately is equipped with level Four and turbine moving blade (blade part) 3.Turbine stator vane 2 at different levels forms the stator blade row of ring-type along turbine circumferentially spaced interval, be separately fixed at turbine shroud 1 side, and towards rotor R _tside is extended.

Similarly, turbine moving blade 3 at different levels forms the moving vane row of ring-type along turbine circumferentially spaced interval, be fixed on rotor R _trotor disk 4A～4D, and extend towards turbine shroud 1 side.

As shown in Figure 2, rotor R _trotor disk 4A～4D that to possess along turbine shaft to coincidence be the axle shape from whole observation.These rotor disks 4A～4D is fixed on periphery separately by the turbine moving blade 3A～3D of the first order～fourth stage.In addition, in the following description, about reference character 3A～3D, 4A～4D, 7A～7D, when referring to particular elements individually, mark capitalization after reference character, when referring to nonspecific parts, omit capitalization.

In these rotor disks 4A～4D along turbine shaft to being formed with the manifold 5 circumferentially extended along turbine between two adjacent rotor disks.In addition, at the upstream side of the rotor disk 4A of the first order, central shaft towards turbine shaft to seal disc 6 with rotor disk 4A, be connected, be formed with manifold 5 between sealing dish 6 and rotor disk 4A.

These manifolds 5 connect continuously via the attachment hole 5a bored a hole respectively at rotor disk 4A～4C and seal disc 6, and the pressurized air c extracted out from compressor C flows into successively from each manifold 5 of seal disc 6 side direction.

And, be formed with radial hole 7A～7D at rotor disk 4A～4D, these radial holes 7A～7D guides to the cooling flowing path 50(of the inside that is formed at each turbine moving blade 3A～3D with reference to Fig. 3 by pressurized air c from the manifold 5 of upstream side separately).These radial holes 7A～7D is formed with a plurality of along turbine circumferentially spaced compartment of terrain respectively on rotor disk 4A～4D.

Fig. 3 is dissecing and the sectional view (the II-II line sectional view in Fig. 4) that forms along aerofoil profile center line Q of turbine moving blade 3, and Fig. 4 is the aerofoil profile sectional view (the III-III line sectional view in Fig. 3) intersected with the width of blade direction of turbine moving blade 3.

As shown in Figure 3, in turbine moving blade 3, blade body 10, platform (end wall) 20, root of blade 30 form according to above-mentioned order continuously from another lateralization of the width of blade direction of blade body 10.

Blade body 10 as shown in Figure 3, makes the width of blade direction towards turbine radially, and as shown in Figure 2, from being formed at rotor disk 4(4A～4D) shown in cardinal extremity (end) 14(Fig. 3 of side) extend to the front end 15 that is positioned at turbine shroud 1 side.

And blade body 10 as shown in Figure 4, makes the vane thickness direction circumferential towards turbine, on the aerofoil section intersected with the width of blade direction, leading edge 11 forms with fillet, and trailing edge 12 forms tip shape.And as shown in Figure 4, on blade body 10, back side 13a is formed at the circumferential side of turbine of blade surface 13 with being convex, outside of belly 13b is formed at the circumferential opposite side of turbine with being concavity.

As shown in Figure 3, platform 20 is with respect to the cardinal extremity 14 of blade body 10 and form continuously to a side at turbine shaft, and extends in the mode of intersecting with the width of blade direction.

The cardinal extremity 14 of this platform 20 and blade body 10 is connected smoothly by fillet part 40.This fillet part 40 becomes circle-shaped along the aerofoil section outline-shaped of cardinal extremity 14, along the width of blade direction, dissect and the cross section profile that forms is quadrant arcuation (with reference to Fig. 6 and Fig. 7).

As shown in Figure 3, root of blade 30 with respect to platform 20 and turbine radially a side (turbine shaft P side) form continuously, form for example Christmas trees shape, triangular shaped.This root of blade 30 is chimeric with the not shown blade root groove of the periphery that is formed at rotor disk 4, and is limited in the peripheral part (with reference to Fig. 2) of rotor disk 4.

Inside at the turbine moving blade 3 consisted of said structure is formed with cooling flowing path 50.

As shown in Figures 3 and 4, cooling flowing path 50 possesses the front edge side stream 51 configured successively towards trailing edge 12 from leading edge 11,

snakelike stream

52,53.

Front edge side stream 51 extends to the front end 15 of blade body 10 in the side than

snakelike stream

52,53 forward edge 11 from root of blade 30 along the width of blade direction.The upstream extremity of this front edge side stream 51 is connected to radial hole 7(with reference to Fig. 2) the importing stream 51i that is communicated with.And front edge side stream 51 is communicated with a plurality of Cooling Holes 51h of the stream wall of the blade surface 13 that connects respectively leading edge 11 and front edge side stream 51.

The pressurized air c of the front end 15 of front edge side stream 51 by flowing to blade body 10 from radial hole 7 and leading edge 11 is carried out cooling, make pressurized air c flow out and that leading edge 11 is carried out to air film (showerhead film) is cooling from Cooling Holes 51h.

Snakelike stream 52 as shown in Figures 3 and 4, form tortuous shape (with reference to Fig. 3) between front edge side stream 51 and snakelike stream 53 in the mode on aerofoil profile center line Q, three primary flow path 52a～52c that extend along the width of blade direction are respectively connected by turn back stream 52d, the 52e that form the U font.

Article three, primary flow path 52a～52c extends to respectively the cardinal extremity 14 of blade body 10 from the front end 15 of blade body 10, and towards leading edge 11 sides, is arranged side by side from trailing edge 12 sides according to above-mentioned order.And the outer circumference end of primary flow path 52a is connected by the stream 52d that turns back with the outer circumference end of primary flow path 52b, the interior Zhou Duan of the interior Zhou Duanyu primary flow path 52c of primary flow path 52b is connected by the stream 52e that turns back.And the upstream extremity of primary flow path 52a is connected to radial hole 7(with reference to Fig. 2) the importing stream 52i that is communicated with.And primary flow path 52c is communicated with a plurality of Cooling Holes 52h of the stream inwall that connects respectively blade surface 13 and primary flow path 52c.

In snakelike stream 52, pressurized air c is from importing stream 52i after primary flow path 52a flows into, and by this primary flow path 52a, turning back stream 52d Rotate 180 °, to primary flow path 52b, flows into, by primary flow path 52b, turning back stream 52e Rotate 180 ° and flowing into to primary flow path 52c.In this process, in primary flow path 52c, as shown in Figure 4, from Cooling Holes, 52h flows out the part of mobile pressurized air c obliquely, blade surface 13 is carried out to air film cooling.

Snakelike stream 53 as shown in Figures 3 and 4, form tortuous shape (with reference to Fig. 3) in the mode be positioned on aerofoil profile center line Q in trailing edge 12 sides, three primary flow path 53a～53c that extend along the width of blade direction are respectively connected by turn back stream 53d, the 53e that form the U font.

Article three, primary flow path 53a～53c extends to respectively the cardinal extremity 14 of blade body 10 from the front end 15 of blade body 10, according to above-mentioned order, from leading edge 11 sides, towards trailing edge 12 sides, is arranged side by side.And the outer circumference end of primary flow path 53a is connected by the stream 53d that turns back with the outer circumference end of primary flow path 53b, the interior Zhou Duan of the interior Zhou Duanyu primary flow path 53c of primary flow path 53b is connected by the stream 53e that turns back.And the upstream extremity of primary flow path 53a is connected to importing stream 53i, the 53j be communicated with radial hole 7.And primary flow path 53c as shown in Figure 4, is communicated with a plurality of Cooling Holes 53h that connect respectively blade surface 13 and primary flow path 53c.

In snakelike stream 53, pressurized air c is from importing stream 53i, 53j after primary flow path 53a flows into, and by this primary flow path 53a, turning back stream 53d Rotate 180 °, to primary flow path 53b, flows into, by primary flow path 53b, turning back stream 53e Rotate 180 ° and flowing into to primary flow path 53c.In this process, in primary flow path 53c, the part of mobile pressurized air c flows out from Cooling Holes 53h to surface and to carry out air film cooling, and remaining pressurized air c is cooling in the turbulence columns (pin-fin) of carrying out the trailing edge end when trailing edge 12 flows out.

In addition, pressurized air c in snakelike stream 53 from importing stream 53i, 53j finally be discharged to combustion gas through

primary flow path

53a, 53b, 53c, turn back

stream

53d, 53e, but in mobile process is turned back at the stream 53d that turns back, 53e place, because making pressure, the pressure loss descends gradually in stream.

In the turbine moving blade 3 that summary forms as mentioned above, above-mentioned turn back

stream

52e, 53e in the turbine footpath upwards across and the cardinal extremity 14 of blade body 10, fillet part 40, platform 20 and form.This turn back

stream

52e, 53e form along fillet part 40 on the cross section intersected with aerofoil profile center line Q.

In addition, turn back

stream

52e, 53e are same structure, and therefore in the following description, doubling backflow road 53e describes, and omit the explanation of the stream 52e that turns back.

Fig. 5 be Fig. 3 want section's enlarged view (enlarged view of wanting the IV of section of Fig. 3), Fig. 6 is the V-V line sectional view of Fig. 5, Fig. 7 is the VI-VI line sectional view of Fig. 5.

As shown in FIG. 6 and 7, the stream 53e that turns back is upper the cross section with aerofoil profile center line Q quadrature (below, referred to as the X-section of aerofoil profile center line Q), with primary flow path 53b and primary flow path 53c, compares, and vane thickness direction size is L shaped becomes to obtain large (L ₁l ₂).And the stream 53e that turns back forms as shown in Figure 6, on the X-section of aerofoil profile center line Q, its width of blade direction size is than the short flat of vane thickness direction size L1.

As shown in Figure 5, be formed with the heat-absorbent surface 55 formed along the outer surface 40a of fillet part 40 in the vane thickness direction both sides of the stream internal face (internal surface) of the stream 53e that turns back.

Heat-absorbent surface 55 extends along aerofoil profile center line Q, and as shown in FIG. 6 and 7, on X-section, along the outer surface 40a of the fillet part 40 that forms the quadrant arcuation, forms circular-arc.More specifically, heat-absorbent surface 55 as shown in Figure 7, on the X-section of aerofoil profile center line Q, position in the front and back of the partition wall 54 that primary flow path 53b and primary flow path 53c are separated, the cross section profile that there is the quadrant arcuation along fillet part 40, and, in the position that comprises partition wall 54 (intermediate portion 53e1), as shown in Figure 6, there is the cross section profile of roundlet arcuation along fillet part 40.

As shown in FIG. 6 and 7, preferably make to form the flow path width (L of the stream 53e that turns back ₁) stream inwall 60 spread near the outer rim 40b of fillet part 40 roughly.Centered by aerofoil profile center line Q and make flow path width (L ₁) towards the both sides of vane thickness direction, spread near the outer rim 40b of fillet part 40, make thus heat-absorbent surface 55 expand on the vane thickness direction along fillet part 40.In addition, the outer rim 40b of fillet part 40 refers to the boundary line between the surface of fillet part 40 and platform 20.

And, when the distance definition of the stream internal face of outer surface on the Normal direction of the outer surface by turbine moving blade 3, this turbine moving blade 3 and cooling flowing path 50 is blade wall wall thickness d, the blade wall wall thickness d between heat-absorbent surface 55 and fillet part 40 ₁at each position, roughly be formed uniformly.

And, the blade wall wall thickness d between heat-absorbent surface 55 and fillet part 40 ₁form the blade wall wall thickness d with primary flow path 53b and primary flow path 53c ₂roughly the same.

And, being formed with protuberance 56 in root of blade 30 sides of the stream internal face of the stream 53e that turns back, this protuberance 56 is outstanding to the Normal direction of stream internal face in vane thickness direction center side.As shown in Figure 6, protuberance 56 is trapezoidal shape on each X-section of aerofoil profile center line Q.As shown in Figure 5, this protuberance 56 in the stream 53e that turns back, overhang along with from primary flow path 53b side direction intermediate portion 53e1 near and after increasing progressively, overhang along with from intermediate portion 53e1 to primary flow path 53c near and successively decrease.

This protuberance 56, except the guiding function of pressurized air c with following explanation, also has the adjustment function of the flowing path section of the stream 53e that turns back.In the present embodiment, by the flow path width (L of the stream 53e that makes as described above to turn back ₁) along the vane thickness direction, widen, pressurized air c, in the central flows of stream 53e of turning back, arranges with the Uniform Flow of guaranteeing flowing path section for fear of producing mobile stagnation near the stream inwall 60 of intermediate portion 53e1.

Next, the effect of the turbine moving blade 3 in the gas turbine GT of said structure is described.

As described above, when pressurized air c flows into to snakelike stream 53 via importing stream 53i, 53j, by primary flow path 53a, turning back stream 53d Rotate 180 °, to primary flow path 53b, flow into, by primary flow path 53b, turning back stream 53e Rotate 180 ° and flowing into to primary flow path 53c.

In the pressurized air c by the stream 53e that turns back, due at heat-absorbent surface 55 upper blade wall wall thickness d ₁roughly be formed uniformly, therefore at each position of fillet part 40, absorb equably heat.

That is, as shown in Figure 5, on the bearing of trend of aerofoil profile center line Q, each position to fillet part 40 is carried out cooling equably.And, on each X-section of aerofoil profile center line Q (with reference to Fig. 6 and Fig. 7), owing to making flow path width (L ₁) spread near the outer rim of fillet part 40, therefore can on the whole width of blade direction of fillet part 40 and vane thickness direction, to each position, carry out cooling equably.

And the closer to intermediate portion 53e1, overhang is larger due to protuberance 56, the pressurized air c that therefore in the stream 53e that turns back, has arrived the upstream extremity of protuberance 56 is directed to the both sides of vane thickness direction immediately.In the stream 53e that turns back, the pressurized air c that is directed to the both sides of vane thickness direction mainly absorbs heat and carries out cooling from fillet part 40 via heat-absorbent surface 55.

And, by adjusting the overhang of protuberance 56, the inhomogeneous of pressurized air c that can improve the flowing path section of the stream 53e that turns back flowed.

As described above, according to the turbine moving blade 3 in gas turbine GT, the stream 53e that turns back forms along fillet part 40 on the X-section of aerofoil profile center line Q, therefore from the stream 53e that turns back, to the blade wall wall thickness d of the outer surface 40a of fillet part 40, becomes even.Thus, can suppress to produce this situation of position that blade wall wall thickness d increases, thereby can evenly and fully carry out cooling to fillet part 40.Therefore, can be suppressed at oxidation attenuate, the fatigue that turbine moving blade 3 produces.In addition, also can in the stream 52e that turns back, obtain same effect.

And, owing to thering is heat-absorbent surface 55, therefore can be more fully to carrying out cooling with this heat-absorbent surface 55 fillet part 40 dorsad.

And owing to having protuberance 56, so pressurized air c is directed to vane thickness direction both sides.Thus, can be fully to the fillet part 40 of the vane thickness direction both sides that are positioned at the stream 53e that turns back, carry out cooling.

And, heat-absorbent surface 55 is roughly the same to the distance of the outer surface of blade body 10 apart from the stream internal face apart from forming with from

primary flow path

53b, 53c of the outer surface 40a of fillet part 40, therefore can between blade body 10 and fillet part 40, carry out equably cooling.

And, because heat-absorbent surface 55 extends along aerofoil profile center line Q, therefore can along aerofoil profile center line Q, form on a large scale in evenly and fully to fillet part 40, carry out cooling.

And, owing to possessing above-mentioned turbine moving blade 3, therefore can improve the cooling effect of turbine moving blade 3, and improve reliability.

(the second mode of execution)

Below, use accompanying drawing, the second mode of execution of the present invention is described.In addition, in the accompanying drawing that the following description and this explanation are used, the same structural element to the structural element with having illustrated, mark same reference character, and the repetitive description thereof will be omitted.

Fig. 8 is the dissecing and the sectional view that forms along the aerofoil profile center line of turbine stator vane 2 of present embodiment.

In the first above-mentioned mode of execution, the present invention is applicable to turbine moving blade 3, and with respect to this, in the present embodiment, the present invention is applicable to the turbine stator vane 2(of turbine T with reference to Fig. 2).

As shown in Figure 8, turbine stator vane 2 engages outside mask (end wall) 2b is arranged at the cardinal extremity (turbine radial outside, end) 58 of blade body 2a, at the front end (turbine radially inner side, end) 59 of blade body 2a, engages inboard cover (end wall) 2c is arranged.

The cardinal extremity 58 of blade body 2a is connected by fillet part 41 smoothly with outside mask 2b, and the front end 59 of blade body 2a is connected by fillet part 42 smoothly with inboard cover 2c.

Be formed with snakelike stream (cooling flowing path) 57 in the inside of this turbine stator vane 2.

Snakelike stream 57 is to be positioned at the mode on the aerofoil profile center line Q shown in Fig. 4, form tortuous shape as shown in Figure 8 between leading edge 11 and trailing edge 12, five primary flow path 57a～57c, 57f that extend along the width of blade direction respectively, 57g are by turn back stream 57d(57dA, the 57dB that form the U font), 57e(57eA, 57eB) connect.

Article five, primary flow path 57a～57c, 57f, 57g extend to respectively front end 59 sides of blade body 2a from cardinal extremity 58 sides of blade body 2a, and towards trailing edge 12 sides, are arranged side by side from leading edge 11 sides according to above-mentioned order.And the interior Zhou Duan of the interior Zhou Duanyu primary flow path 57b of primary flow path 57a is connected by the stream 57eA that turns back, the outer circumference end of primary flow path 57b is connected by the stream 57dA that turns back with the outer circumference end of primary flow path 57c.And the interior Zhou Duan of the interior Zhou Duanyu primary flow path 57f of primary flow path 57c is connected by the stream 57eB that turns back, the outer circumference end of primary flow path 57f is connected by the stream 57dB that turns back with the outer circumference end of primary flow path 57g.

And the upstream extremity of primary flow path 57a is communicated with the blade ring sprocket hole 70 of supplying with pressurized air c, primary flow path 57g is communicated with the Cooling Holes 53m of trailing edge 12, the trailing edge end has been carried out convection current cooling after, pressurized air c is discharged in combustion gas.

Above-mentioned turn back stream 57d(57dA, 57dB), 57e(57eA, 57eB) mode along

fillet part

41,42 on the cross section that intersects with the aerofoil profile center line with blade body 2a forms.

More specifically, at turn back stream 57d(57dA, 57dB separately), 57e(57eA, 57eB) in, be formed with heat-absorbent surface 55 along the outer surface of fillet part 41,42.And, be formed with protuberance 57d1 in the stream 57d that turns back, this protuberance 57d1 is outstanding to the Normal direction of stream internal face in vane thickness direction center side, be formed with protuberance 57e1 in the stream 57e that turns back, this protuberance 57e1 is outstanding to the Normal direction of stream internal face in vane thickness direction center side.

According to present embodiment, except the main effect that can obtain above-mentioned the first mode of execution, can also be fully to the

fillet part

41,42 of turbine stator vane 2, carry out cooling.

In addition, each shape of the action step illustrated in the above-described embodiment or each structure member, combination etc. are examples, can in the scope that does not break away from purport of the present invention, based on designing requirement etc., carry out various changes.

For example, in the first above-mentioned mode of execution, on the X-section of aerofoil profile center line Q, heat-absorbent surface 55 is formed to circular-arc cross section profile and along the outer surface of fillet part 40, but also can form the straight line shape extended obliquely along the tangent direction of the outer surface of fillet part 40 cross section profile and along the outer surface of fillet part 40.In the second mode of execution too.

And, in the first above-mentioned mode of execution, the present invention be applicable to turn back

stream

52e, 53e, but the present invention also can be only applicable to the either party.And, also can form a plurality of and same stream that turns back of

stream

52e, 53e that turns back, and the present invention is applicable to wherein at least one.In the second mode of execution too.

(the 3rd mode of execution)

Below, use accompanying drawing, the 3rd mode of execution of the present invention is described.In addition, in the accompanying drawing that the following description and this explanation are used, the same structural element to the structural element with having illustrated, mark same reference character, and the repetitive description thereof will be omitted.

Present embodiment is that the embodiment of Cooling Holes is set at the reflex part of above-mentioned snakelike stream, can be applicable to first and second mode of execution both sides.Fig. 9 is the figure that the partition wall of upstream side of the flow direction of the pressurized air c that illustrated at each reflex part entrance in the blade view of the turbine moving blade same at the Fig. 3 with the first mode of execution is provided with the example of Cooling Holes.Figure 10 be Fig. 9 want section's enlarged view (enlarged view of wanting the VII of section of Fig. 9).Figure 11 means the figure of the cross section VIII-VIII observed on the leading edge direction around the stream 53e that turns back of Figure 10, and Figure 12 means the figure of the stream 53e cross section IX-IX on every side that turns back of Figure 11.Below, by Fig. 9 to Figure 12, take the stream 53e that turns back of snakelike stream 53 as example, present embodiment is described.

Fig. 9 and Figure 10 show following example: near the cardinal extremity 14 of snakelike stream 53, the partition wall 54 of being separated between to

primary flow path

53a and 53b arranges Cooling Holes 53k, and this Cooling Holes 53k is towards the configuration of the inclined bottom surface ground of the stream 53e that turns back.

And, as shown in figure 11, the flowing path section formed by the stream inwall 60 of the both sides of the vane thickness direction of the stream 53e that turns back, in the sectional view of width of blade direction, flow path width (L1) spreads near the outer rim 40b of fillet part 40, for the stream inwall 60 blowing out pressurised air c towards the both sides widened, and dispose two Cooling Holes 53k near the dorsal part of primary flow path 53b and veutro.A Cooling Holes 53k is communicated with the upstream side stream of the primary flow path 53a of the upstream side of snakelike stream 53, and another Cooling Holes 53k is the primary flow path 53b opening of side downstream.

As shown in figure 12, the stream of the stream 53e that turns back is the shape that possesses enlarged portion 61, and dorsal part and the veutro of this enlarged portion 61 from the stream of

primary flow path

53b and 53c to the vane thickness direction expands.Keep tilting with respect to aerofoil profile center line Q at dorsal part separately and the set Cooling Holes 53k of veutro, and make pressurized air c towards the direction that blows to stream inwall 60.

As described above, the pressure loss produced in mobile process in stream due to pressurized air c mobile in snakelike stream, so the pressure drop of pressurized air c.If the snakelike stream 53 of take describes as example, mobile towards front end 15 from terminal side 14 to the pressurized air c of the low temperature of primary flow path 53 inflows from importing stream 53i, 53j, at reflex part 53d Rotate 180 ° and turn back, and then flow down and arrive reflex part 53e, the pressure drop due to the pressure loss in stream during this period towards cardinal extremity 14.; near the entrance of the stream 53e that turns back in the downstream side of the upstream side cardinal extremity 14 of primary flow path 53a and primary flow path 53b; because the pressure loss produces certain pressure difference; therefore due to the pressure difference of inlet side and the outlet side of Cooling Holes 53k, in primary flow path 53a, the part of mobile pressurized air c flows through Cooling Holes 53k and blows out to the stream 53e that turns back.

According to present embodiment, pressurized air c may stagnate the enlarged portion 61 expanded to the vane thickness direction on the flowing path section of the stream 53e that turning back, but by the Cooling Holes 53k of present embodiment is set, the part of pressurized air c is towards the stream inwall 60 of the stream 53e that turns back and oliquely downward blow out to (interior side direction radially), therefore be stranded in enlarged portion 61 stagnation pressurized air downstream side be eliminated, pressurized air stream at heat-absorbent surface 55 Flow Structure Nearbies of the stream 53e that turns back is updated, and the cooling performance of heat-absorbent surface 55 improves.

Similarly, also can be in the stream 52e that turns back of snakelike stream 52, the partition wall 54 between

primary flow path

52a and 52b arranges Cooling Holes 52k, the applicable and same structure of stream 53e of turning back.

And the present invention is applicable to the turbine moving blade 3 of above-mentioned turbine T and the turbine stator vane 2 of turbine T, but also the present invention can be applicable to moving vane and the stator blade (for example moving vane of compressor C and stator blade (with reference to Fig. 1)) of various rotating machineries.

Industrial applicibility

The present invention relates to a kind of blade part, possess: blade body; End wall, be located at the end on the width of blade direction of above-mentioned blade body, and extend in the mode of intersecting with above-mentioned width of blade direction; Fillet part, be connected the end of above-mentioned blade body smoothly with above-mentioned end wall; And cooling flowing path, make the internal circulation of cooling medium at above-mentioned blade body and above-mentioned end wall, and two primary flow path of extending along above-mentioned width of blade direction are connected in the mode bent by the stream that turns back that is formed at above-mentioned end wall side, in above-mentioned blade part, the above-mentioned stream that turns back forms in the mode along above-mentioned fillet part on the cross section intersected with the aerofoil profile center line of above-mentioned blade body, and the width of the vane thickness direction of the above-mentioned stream that turns back forms greatlyr than the flow path width of the vane thickness direction of above-mentioned primary flow path.According to the present invention, can evenly and fully carry out cooling at fillet part.

Description of reference numerals

2 ... turbine stator vane (blade part)

2a ... blade body

2b ... outside mask (end wall)

2c ... inboard cover (end wall)

3(3A～3D) ... turbine moving blade (blade part)

10 ... blade body

14 ... cardinal extremity (end)

20 ... platform (end wall)

40 ... fillet part

41 ... fillet part

42 ... fillet part

40a ... outer surface

50 ... cooling flowing path

52b, 52c ... primary flow path

52e ... stream turns back

52k, 53k Cooling Holes

53b, 53c ... primary flow path

53e ... stream turns back

55 ... heat-absorbent surface

56 ... protuberance

57 ... snakelike stream (cooling flowing path)

57a～57c, 57f, 57g ... primary flow path

57d(57dA, 57dB), 57e(57eA, 57eB) ... stream turns back

58 ... cardinal extremity (end)

59 ... front end (end)

60 stream inwalls

61 enlarged portion

C ... compressor (rotating machinery)

GT ... gas turbine (rotating machinery)

Q ... the aerofoil profile center line

T ... turbine (rotating machinery)

C ... pressurized air (cooling medium)

Claims

1. a blade part possesses:

Blade body;

End wall, be located at the end on the width of blade direction of described blade body, and extend in the mode of intersecting with described width of blade direction;

Fillet part, be connected the end of described blade body smoothly with described end wall;

Cooling flowing path, make the internal circulation of cooling medium at described blade body and described end wall, and two primary flow path of extending along described width of blade direction are connected in the mode bent by the stream that turns back that is formed at described end wall side,

The described stream that turns back forms in the mode along described fillet part on the cross section intersected with the aerofoil profile center line of described blade body, and the width of the vane thickness direction of the described stream that turns back forms greatlyr than the flow path width of the vane thickness direction of described primary flow path.

2. blade part according to claim 1, wherein,

The described stream that turns back has the heat-absorbent surface formed along the outer surface of described fillet part in surface within it.

3. blade part according to claim 1, wherein,

The described stream that turns back has protuberance, and described protuberance is formed at the center side of the vane thickness direction of described blade body, and the flow direction of described cooling medium is guided to described vane thickness direction both sides.

4. blade part according to claim 1, wherein,

Possess Cooling Holes on the described partition wall of stream between the upstream side stream in itself and described primary flow path that turn back, the upstream side stream in wherein said primary flow path is positioned at the upstream side of the described stream that turns back.

5. blade part according to claim 2, wherein,

The distance of the outer surface apart from described fillet part of described heat-absorbent surface forms with the outer surface from described blade body roughly the same to the distance of the internal surface of described primary flow path.

6. blade part according to claim 2, wherein,

Described heat-absorbent surface extends along described aerofoil profile center line.

7. a rotating machinery, possess blade part claimed in claim 1.